US20200346777A1 - Fuselage and unmanned aerial vehicle thereof - Google Patents

Fuselage and unmanned aerial vehicle thereof Download PDF

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Publication number
US20200346777A1
US20200346777A1 US16/932,497 US202016932497A US2020346777A1 US 20200346777 A1 US20200346777 A1 US 20200346777A1 US 202016932497 A US202016932497 A US 202016932497A US 2020346777 A1 US2020346777 A1 US 2020346777A1
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US
United States
Prior art keywords
disposed
control board
uav
core control
fuselage
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Abandoned
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US16/932,497
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English (en)
Inventor
Zhao Tong
Jiangang FENG
Yin Tang
Yumian Deng
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
SZ DJI Technology Co Ltd
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SZ DJI Technology Co Ltd
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Filing date
Publication date
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Assigned to SZ DJI Technology Co., Ltd. reassignment SZ DJI Technology Co., Ltd. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: FENG, Jiangang, TANG, YIN, TONG, ZHAO, DENG, Yumian
Publication of US20200346777A1 publication Critical patent/US20200346777A1/en
Abandoned legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/19—Propulsion using electrically powered motors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D31/00—Power plant control systems; Arrangement of power plant control systems in aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C19/00—Aircraft control not otherwise provided for
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/40—Alighting gear characterised by elements which contact the ground or similar surface  the elements being rotated before touch-down
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/02—Aircraft not otherwise provided for characterised by special use
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D47/00—Equipment not otherwise provided for
    • B64D47/08—Arrangements of cameras
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U20/00—Constructional aspects of UAVs
    • B64U20/90—Cooling
    • B64U20/92—Cooling of avionics
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/20—Rotors; Rotor supports
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
    • H05K7/00—Constructional details common to different types of electric apparatus
    • H05K7/20—Modifications to facilitate cooling, ventilating, or heating
    • H05K7/20009—Modifications to facilitate cooling, ventilating, or heating using a gaseous coolant in electronic enclosures
    • H05K7/20136—Forced ventilation, e.g. by fans
    • H05K7/20172—Fan mounting or fan specifications
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
    • H05K7/00—Constructional details common to different types of electric apparatus
    • H05K7/20—Modifications to facilitate cooling, ventilating, or heating
    • H05K7/20845—Modifications to facilitate cooling, ventilating, or heating for automotive electronic casings
    • H05K7/20863—Forced ventilation, e.g. on heat dissipaters coupled to components
    • B64C2201/027—
    • B64C2201/145—
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/13—Flying platforms
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/13—Flying platforms
    • B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U2201/00—UAVs characterised by their flight controls
    • B64U2201/10—UAVs characterised by their flight controls autonomous, i.e. by navigating independently from ground or air stations, e.g. by using inertial navigation systems [INS]
    • B64U2201/104—UAVs characterised by their flight controls autonomous, i.e. by navigating independently from ground or air stations, e.g. by using inertial navigation systems [INS] using satellite radio beacon positioning systems, e.g. GPS
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/30—Supply or distribution of electrical power

Definitions

  • the present disclosure relates to the field of unmanned aerial vehicles and, more specifically, to a fuselage and an unmanned aerial vehicle (UAV).
  • UAV unmanned aerial vehicle
  • the assembly position of the battery of the UAV is located above the fuselage, and the battery can be assembled into the fuselage from the top of the fuselage.
  • the battery weight of the UAV is relatively heavy, generally accounting for substantially one third of the weight of the UAV.
  • the present disclosure provides an UAV.
  • the UAV includes a fuselage including a housing, a core control board disposed in the housing, and a battery, the housing including a battery compartment, and the battery being disposed in the battery compartment; an arm disposed on the fuselage; and a power assembly disposed on the arm.
  • the core control board is disposed above the battery, a payload receiving cavity is disposed at a front lower end of the housing, a rear-bottom view component is disposed at a rear end of the housing and electrically connected to the core control board, and the battery compartment is disposed at a middle position under the housing.
  • FIG. 1 is a perspective view of a UAV according to an embodiment of the present disclosure.
  • FIG. 2 is an exploded perspective view a fuselage of the UAV shown in FIG. 1 .
  • FIG. 3 is an exploded perspective view of the fuselage shown in FIG. 2 from another perspective.
  • FIG. 4 is a partial cross-sectional view at the position of a landing gear of the UAV shown in FIG. 1 .
  • a UAV 200 can be used for aerial photography, mapping, monitoring, but is not limited thereto. In some embodiments, the UAV can also be used for agriculture, express delivery, and providing network services.
  • the UAV 200 includes a fuselage 100 , an arm 300 disposed on the fuselage 100 , a power assembly 400 disposed on the arm 300 , and a landing gear 500 .
  • the power assembly 400 may include a rotor 45 and a motor 46 .
  • the rotor 45 may be driven to rotate by the motor 46 , thereby providing power for the lift, advancement, rotation, etc. of the UAV 100 .
  • the rotor 45 may include a blade and a hub, the hub may be fixed to an output shaft of the motor, and the blade may be mounted on the hub.
  • the fuselage 100 may include a housing 10 , a core control board 20 disposed in the housing 10 , and a battery 30 .
  • a battery compartment 11 may be disposed in the housing, and the battery may be disposed in the battery compartment 11 .
  • the core control board 20 may be positioned above the battery 30 , and payload receiving cavity 16 may be disposed at the front lower end of the housing.
  • a rear-bottom view component 52 may be disposed in the rear of the housing 10 .
  • the rear-bottom view component 52 may be electrically connected to the core control board 20 , and the battery compartment 11 may be disposed at a middle position under the housing 10 . Since the weight of the battery is relatively heavy, the center of gravity of the UAV 200 can be centered and lowered, which can improve the flight stability of the UAV.
  • the battery compartment 11 is recessed from a bottom surface 131 of the housing 10 , and the battery 30 is mounted in the battery compartment 11 through a locking structure.
  • the locking structure may include a locking pin 31 slidably disposed on both sides of the battery, a locking groove 111 disposed at a corresponding position on an inner wall of the battery compartment 11 , and an elastic member (not shown) at one end of the lock pin 31 .
  • the elastic member can push the locking pin 31 to make the locking pin 31 snap in to the locking groove 111 , thereby fixing the battery 30 in the battery compartment 11 .
  • the locking structuring may also include other structures, which is not limited herein.
  • the housing 10 may include a housing body 13 and a cover 14 .
  • the housing body 13 may include a top surface 132 opposite to the bottom surface 131 .
  • a receiving cavity 12 may be disposed on the top surface 132 for receiving the core control board 20 , and the cover 14 may be used to close the core control board 20 in the receiving cavity 12 .
  • a protrusion 141 that extends to the bottom of the housing body 13 may be disposed on the cover 14 .
  • a recess 136 may be provided on the housing body 13 to cooperate with the protrusion 141 .
  • the cover 14 and the housing body 13 may be connected with each other, thereby increasing the strength of the UAV 200 .
  • the core control board 20 may be electrically connected to each functional module of the UAV 200 and coordinates the work of each functional module.
  • the core control board 20 is positioned between the battery 30 and the cover 14 , that is, in the middle of the fuselage 100 . As such, the distance between the core control board 20 and each functional module is reduced, thereby reducing the internal wiring and optimizing the internal space arrangement of the UVA 200 .
  • the fuselage may also include an electronic speed control board 40 .
  • the electronic speed control board 40 may be configured to control the operation of the motor.
  • the electronic speed control board 40 may be electrically connected to the core control board 20 to control the start and stop, the rotational speed, the steering, etc. of the motor based on the control signal sent by the core control board 20 , thereby controlling the flight direction and flight speed of the UAV 200 .
  • the electronic speed control board 40 is disposed at the bottom of the receiving cavity 12
  • the core control board 20 is disposed above the electronic speed control board 40 . Therefore, as the core components of the UAV 200 , the electronic speed control board 40 and the core control board 20 may be both positioned in the middle of the fuselage 100 . When the UAV 200 receives an impact, the UAV 200 cannot be easily damaged.
  • the fuselage 100 may further include a front view assembly 51 electrically connected to the core control board 20 .
  • the front view assembly 51 may be disposed at the front of the housing 10 .
  • the front view assembly 51 may be used to detect obstacles in front of the UAV 200 , and send the detection data to the core control board 20 .
  • the rear-bottom view assembly 52 describe above may be used to detect obstacles behind and below the UAV 200 , and send the detection data to the core control board 20 .
  • the front view assembly 51 and the rear-bottom view assembly 52 may be positioned blow the core control board 20 , which can further lower the center of gravity of the UAV 200 and improve flight stability. In other embodiments, the front view assembly 51 and the rear-bottom view assembly 52 may be positioned at other positions, such as at the same height as the core control board 20 , but is not limited thereto.
  • the front view assembly 51 and the rear-bottom view assembly 52 may be respectively connected to the core control board 20 through a flexible circuit board, but is not limited thereto.
  • the fuselage 100 may further include a payload 60 electrically connected the core control board 20 , and the payload 60 may be disposed in the payload receiving cavity 16 .
  • the payload 60 may be positioned below the core control board 20 , which can further lower the center of gravity of the UAV 200 and improve flight stability. In other embodiments, the payload 60 may be positioned at other positions, such as at the same height as the core control board 20 , but is not limited thereto.
  • the payload 60 may include a gimbal and an imaging device carried on the gimbal, and the payload 60 may be connected to the core control board 20 through a flexible circuit board.
  • the core control board 20 may include a board fuselage 21 , and a circuit assembly 23 disposed on the board fuselage 21 .
  • the circuit assembly 23 may include a flight control module, a vision module, and an imaging module.
  • the flight control module is the core component of the UAV 200 .
  • the flight control module can be used to control the main functions of the UAV 200 as the central controller of the UAV 200 .
  • the flight control module can be used to manage the working mode of the control system of the UAV 200 , perform calculation on the data sent by the vision module, the imaging module, and various sensors to the flight control module and generate control signals, manage various sensors and servo systems in the UAV 200 , control and perform data exchange of other tasks and electronic components in the UAV 200 , receive ground commands to control the flight actions of the UAV and acquire the attitude information of the UAV 200 , etc.
  • the vision module can be used to process the visual image data from the image sensor based on a certain computer vision algorithm, and send the processing results to the flight control module for the flight control module to make obstacle avoidance or navigation decisions.
  • the imaging module can be used to process the aerial image data from the image sensor based on different needs by using the corresponding algorithm to meet the subsequent storage or transmission needs, and can simultaneously output multiple channels of data to meet different needs.
  • the core control board 20 may further include a positioning module 24 .
  • the positioning module 24 is a GPS module.
  • the GPS module is positioned on the side of the core control board 20 away from the battery compartment 11 .
  • the positioning module 24 can also be other modules, such as the Beidou positioning module, etc., which is not limited thereto.
  • the core control board 20 may further include a gimbal control module.
  • the gimbal may be connected to the gimbal control module, and the gimbal control module may be electrically connected to the flight control module to facilitate communication between the gimbal and the flight control module to control and drive the gimbal.
  • the gimbal can be connected to the gimbal control module through a flexible circuit board.
  • the fuselage may further include a heat dissipation structure.
  • the heat dissipation structure will be described below.
  • a first air outlet 151 and a second air outlet 152 for heat dissipation of the core control board 20 may be disposed on the housing 10 .
  • the first air outlet 151 may be used introduce the airflow outside the fuselage from the first air outlet 151 into the housing, and the second air outlet 152 may be used direct the airflow out of the housing 10 after heat transfer is performed with the core control board 20 .
  • the side projection of the first air outlet 151 may at least partially overlap with the side projection of the rotor 45 .
  • the direction of the side projection mentioned above may refer to the side direction of the fuselage. It can be understood that direction of the side projection mentioned above may refer to the direction of the side of the fuselage of the UAV. That is, when projecting on the fuselage side of the UAV, the projection of the first air outlet 151 and the projection of the rotor 45 may at least partially overlap.
  • the rotation of the rotor 45 can form a plane of rotation.
  • the rotation of the rotor 45 may cause the surrounding air to move in the direction of rotation of the rotor 45 .
  • a part of the airflow around the rotor 45 may be detached from the surface of the rotor 45 and run along the tangential direction of the plane of rotation due to air resistance.
  • the air around the rotor 45 may also be directed below the plane of rotation to form downwash airflow.
  • the airflow running along the tangential direction of the plane of rotation, and/or the downwash airflow running along the plane of rotation may enter the housing 10 through the first air outlet 151 .
  • the UAV generally flies at a relatively high altitude, and the temperature of the surrounding air is generally low. Therefore, the low temperature airflow entering the housing 10 from the first air outlet 151 may can play a good role in cooling and heat dissipation of the core control board 20 without increasing the noise of the UAV 200 .
  • the first air outlet 151 is disposed on the cover 14 . Based on the rotor 45 and other height designs on the top of the UAV 200 , the first air outlet 151 may also be disposed on the sidewall of the UAV 200 , which is no limited herein.
  • the fuselage 100 may also include a heat dissipation assembly for active heat dissipation.
  • the heat dissipation assembly may disposed on the core control board 20 and may include a cooling fan 71 and a plurality of heat dissipation fins 72 .
  • the cooling fan 71 may be disposed near the second air outlet 152 , and may be used to draw airflow into the fuselage through the second air outlet 152 .
  • the plurality of heat dissipation fins 72 may be disposed near the second air outlet 152 .
  • the airflow may flow through the plurality of heat dissipation fins 72 and discharge through the second air outlet 152 .
  • the core control board 20 may further include a split flow module.
  • the split flow module may split the cooling airflow, such that the cooling airflow can be discharged from the fuselage more effectively.
  • the positioning module 24 disposed on the core control board 20 may be near the first air outlet 151 , and may be used to distribute and guide the passing cooling airflow (the cooling airflow may be the airflow generated when the rotor 45 rotates, or the airflow generated when the cooling fan 71 rotates), which can effectively discharge the cooling airflow out of the housing 10 from multiple directions.
  • the cooling airflow can also be guided by other modules or structures.
  • the positioning module 24 may include a first part 241 , and a second part 242 disposed on the first part 241 .
  • the first part 241 and the second part 242 may cooperate to guide the airflow.
  • the second part 242 may be a square structure, and the corners of the square structure may be respectively near the sides of the first part 241 . That is, a pair of adjacent sides of the second part 242 may cooperate with the first part 241 , and a 45° airflow direction may be formed from one side of the first part 241 to the adjacent two sides and form an airflow direction above the second part 242 . As such, the cooling airflow passing through the positioning module 24 may be split into three airflow directions.
  • the extension direction of the two adjacent side surfaces of the square structure may correspond to the direction of the corresponding first air outlet 151 , such that heat can be dissipated more efficiently.
  • the second part 242 may also have other shapes, such as a diamond-shaped structure, etc. As long as the second part 242 has a structure that can divide the guide the cooling airflow, the second part 242 is not limited to a specific shape.
  • the heat dissipation assembly may include a windshield 80 .
  • the windshield 80 may be used to form a closed air passage from the heat dissipation fins 72 to the first air outlet 151 .
  • the windshield 80 may include a first part 81 and a second part 82 .
  • the first part 81 may cover the plurality of heat dissipation fins 72 and close the top of the heat dissipation fins 72 .
  • the second part 82 may have a U-shaped structure, surrounding a side of the positioning module 24 away from the plurality of heat dissipation fins 72 and its adjacent sides.
  • the cooling airflow can be limited to the closed air duct, and discharged from the first air outlet 151 , or the first air outlet 151 and the second air outlet 152 out of the housing 10 to prevent the cooling airflow from spreading to other parts of the housing 10 , thereby improving the cooling efficiency of the electronic components.
  • a windshield protrusion 85 may also be disposed between the cooling fan 71 and the plurality of heat dissipation fins 72 .
  • the material of the windshield protrusion 85 may include, but is not limited to foam.
  • An opening may be disposed on the windshield protrusion 85 corresponding to the air outlet of the cooling fan 71 , and the opening may communicate with the plurality of cooling channels formed by the plurality of heat dissipation fins 72 .
  • the windshield protrusion 85 can separate cold air from the outside and the hot air after heat transfer, thereby improving the cooling efficiency of the cooling fan 71 .
  • the heat dissipation assembly may be fixed on the core control board 20 , and disposed on both sides of the core control board 20 opposite to the circuit assembly 23 .
  • the heat dissipation structure described above can cool the core control board 20 and other electronic components in the fuselage through a variety of cooling methods.
  • the airflow generated by the rotation of the rotor is mainly used for cooling.
  • the airflow may enter the housing 10 from the first air outlet 151 , exchange heat with electronic components, and discharge through the second air outlet 152 .
  • the cooling fan 71 can be turned on to improve the cooling efficiency, or the cooling fan 71 can be turned off.
  • the cooling fan 71 can be turned on to drive the airflow from the second air outlet 152 into the housing 10 . After the airflow exchanges heat with the electronic components, the airflow may be discharges through the first air outlet 151 .
  • the arm 300 may be a foldable arm, which is convenient for transportation and storage.
  • the arm 300 may include a pair first arms 310 disposed at one end of the fuselage and a pair of second arms 320 disposed at the other end of the fuselage.
  • the first arm 310 may rotate relative to the fuselage until the first arm 310 are collapsed outside the fuselage.
  • the second arm 320 may include a connecting arm 321 that ma rotate relative to the fuselage and a support arm 322 that may rotate relative to the length direction of the connecting arm 321 . By rotating the support arm 322 to a certain angle and the rotating the connecting arm 321 , the second arm 320 may be collapsed outside the fuselage, and the rotor 45 and the motor 46 of the first arm 310 may face upward.
  • the interference between the rotor of the first arm 310 and the rotor of the second arm 320 may be avoided after the arm 300 is folded.
  • the first arm 310 may be disposed at the front of the fuselage, and the second arm 320 may be disposed at the rear of the fuselage. In other embodiments, the first arm 310 may be disposed at the rear of the fuselage, and the second arm 320 may be disposed at the front of the fuselage.
  • the length of the first arm 310 and the length of the second arm 320 may not exceed the length of the fuselage. As such, the first arm 310 and the second arm 320 may not interfere after being folded. In addition, the first arm 310 and the second arm 320 may be disposed at substantially the same height or different heights of the fuselage.
  • the UAV 200 furthers include a landing gear 500 having a folded state and an open state.
  • the landing gear 500 may include a bracket 512 connected to the arm 300 , and a leg 510 rotatably connected to the bracket 512 .
  • the landing gear 500 may be in an open state, and when the leg 510 is parallel to the arm, the landing gear 500 may be in a folded state.
  • the leg 510 can be turned first to make the landing gear 500 in the folded state, and then the arm 300 can be folded.
  • the landing gear 500 may further include an antenna board 515 .
  • a receiving cavity 511 may be disposed on the leg 510 for receiving and fixing the antenna board 515 .
  • the antenna board 515 may rotate accordingly.
  • the antenna board 515 may be connected to the core control board 20 through an antenna.
  • the antenna board 515 may receive the wireless communication signal and provide the wireless communication signal to the core control board 20 . Since the antenna board 515 is disposed in the leg 510 , the wireless communication signal of the remote control other control terminal generally comes from the ground (i.e., the wireless communication signal is generally transmitted from below the UAV to the UAV), as such, by disposing the antenna board 515 in the leg 510 below the UAV, it may be more convenient and efficient to receive the wireless communication signal.
  • the landing gear 500 is only disposed on the pair of first arms 310 disposed at the front of the fuselage to raise the gimbal. As such, when the gimbal is performing self-check on the impact limit during takeoff, the imaging device carried on the gimbal may not touch the ground.
  • the landing gear 500 may also be disposed on the pair of second arms 320 at the rear of the fuselage based on the actual needs, or the landing gear 500 may be disposed on both pairs of arms.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Microelectronics & Electronic Packaging (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Remote Sensing (AREA)
  • Toys (AREA)
US16/932,497 2018-01-19 2020-07-17 Fuselage and unmanned aerial vehicle thereof Abandoned US20200346777A1 (en)

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PCT/CN2018/073512 WO2019140660A1 (zh) 2018-01-19 2018-01-19 机身及包括该机身的无人机

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US20200346745A1 (en) * 2018-01-19 2020-11-05 SZ DJI Technology Co., Ltd. Heat dissipation structure, heat dissipation method and device, unmanned aerial vehicle, and readable storage medium
US11034446B2 (en) * 2016-02-29 2021-06-15 SZ DJI Technology Co., Ltd. Power supply assembly
CN113772093A (zh) * 2021-09-17 2021-12-10 中国水利水电科学研究院 跨流域调水工程渡槽用的无人机巡检设备及其巡检方法
US11422436B2 (en) * 2018-06-26 2022-08-23 SZ DJI Technology Co., Ltd. UAV and body thereof, and gimbal camera
US20220340293A1 (en) * 2021-04-27 2022-10-27 Airbus Operations Sas Device for connecting an aircraft engine and a primary structure of an aircraft pylon comprising a rudder and a system for limiting the displacement of the rudder incorporating a double stop, aircraft comprising such a device
US20230154180A1 (en) * 2019-02-11 2023-05-18 Booz Allen Hamilton Inc. Advanced Manufacturing Technologies and Machine Learning in Unmanned Aviation Systems

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KR101644151B1 (ko) * 2016-05-12 2016-08-11 (주)원지리정보 지능형 무인항공기를 이용한 3d공간정보 모니터링 시스템
CN206171808U (zh) * 2016-11-24 2017-05-17 傲飞创新科技（深圳）有限公司 模块化无人机
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CN206691352U (zh) * 2017-05-14 2017-12-01 傲飞创新科技（深圳）有限公司 拼块式无人机
CN207773456U (zh) * 2018-01-19 2018-08-28 深圳市大疆创新科技有限公司 无人机

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